A system for controlling blade tip clearances in a gas turbine engine may comprise an active clearance control system and a controller in operable communication with the active clearance control system. The controller may be configured to identify a cruise condition, reduce a thrust limit of the gas turbine engine to a de-rated maximum climb thrust, determine a first target tip clearance based on the de-rated maximum climb thrust, and send a command signal correlating to the first target tip clearance to the active clearance control system.

An abradable powder composition is includes a metal component, a lubricant component, and a polymer component. A portion of the metal component is wrapped in the lubricant component to achieve high lubricity and abradability. The abradable powder composition can be used to form an abradable seal coating provided for use in a turbo machinery having a housing and a wheel having multiple blades. The housing houses the wheel which rotates therein. The seal coating is formed on the inner walls of housing adjacent where the wheel blades pass during their rotation. When the wheel is rotated such that the blades contact the seal coating, it is abraded to form a close fit gap. The abradable seal coating preferably does not produce significant wear of the blade tips or transfer abradable material significantly to the blade tips upon being abraded.

An airfoil arrangement for a gas turbine engine may include a support device using a shape memory alloy to support and control the airfoil. The support device may be formed as part of a fan blade. The arrangement may be configured to reduce overall weight and dimensions of the gas turbine engine.

A turbine blade that allows an improvement in torque and power, and a turbine and gas turbine including the same are provided. The turbine blade includes an airfoil having a suction side and a pressure side, a platform coupled to a bottom of the airfoil, and a root protruding downward from the platform and coupled to a rotor disk, wherein the airfoil includes a cooling passage formed therein and a discharge hole connected to an upper portion of the cooling passage to discharge cooling air, and the discharge hole is inclined toward a tip of the turbine blade while extending from an inside to an outside thereof.

An electrically powered aerial vehicle includes at least one motor where each motor includes a stator and a rotor, a motor housing having an inlet opening and a discharge opening for airflow, a plurality of rotor blades rotatable by the rotor, each of the plurality of rotor blades having a cavity running from a proximal end of the rotor blade towards a distal end of the rotor blade, and a blade hub coupled to the rotor blades at the proximal end of each rotor blade and coupled to the motor housing at the discharge opening. A chamber is defined in the blade hub and is in fluid communication with the discharge opening of the motor housing and the cavity of each rotor blade. The airflow is centrifugally drawn in from the motor housing through the discharge opening and transported through the chamber and into the cavities of the rotor blades when the rotor blades are rotating.

An apparatus and method for an engine component for a turbine engine. The engine component having an outer wall defining an interior and extending between a root and a tip to define a radial direction, a tip wall spanning the first side and second sides to close the interior at the tip. A tip rail extending from the tip wall and having an inner tip rail surface, an outer tip rail surface extending from at least one of the first or the second side, and radially terminating in an upper tip rail surface connecting the inner tip rail surface and the outer tip rail surface. A tip rim formed in at least one of the outer surface or the inner tip rail surface and spaced from the upper tip rail surface in the radial direction, and multiple cooling passages formed in the outer wall and fluidly coupling the at least one cooling conduit to the tip rim at corresponding passage outlets.

A blade structure with multiple blade angles and a heat dissipation device include: the blade structure consisting of a plurality of blades with different blade angles. The blade angles of the blades decrease from an inner side to an outer side along a longitudinal direction of the blade structure. The blades have top portions on the same surface and are integrally formed in one piece. A joint between the blades has a transition part. The blade structures are evenly mounted on the hub and are connected to an outer frame. The hub and the blade structures are integrally formed in one piece, or the hub, the blade structures, and the outer frame are integrally formed in one piece. The blade structures can guide air flow to reduce air shedding, suppress backflows, reduce vortex turbulence, increase air volume, improve heat dissipation efficiency, and reduce vortex noise and vibration.

An abrasive tip comprises an additive, the additive is configured to prevent adhesion of an organic component from an abradable seal onto an abrasive blade tip.

A method of applying an additive to an abrasive coated blade tip comprises applying the additive to the abrasive coated blade tip and wicking the additive into the abrasive coated blade tip, wherein the additive is configured to prevent adhesion of an organic component of an abradable seal onto the abrasive coated blade tip.

An abradable seal comprises an organic matrix composite comprising an additive and an organic component, the additive is configured to prevent adhesion of the organic component onto an abrasive blade tip.